OMPI – Búsqueda en las colecciones de patentes nacionales e internacionales

1.WO/1997/047179VEGETAL SOIL MIXTURE FOR CULTIVATED TURF AND METHOD FOR PRODUCING THE SAME

WO - 18.12.1997

Clasificación Internacional A01G 1/00 Nº de solicitud PCT/RU1996/000171 Solicitante MYLNIKOV, Vladimir Nikolaevich Inventor/a MYLNIKOV, Vladimir Nikolaevich

The present invention relates to a vegetal soil mixture for cultivated turf that also comprises a rocky material, preferably marble crumbs having a fraction size between 3 and 10 mm. This mixture comprises the following components in wt.%: from 60 to 80 % of sandy or clayey soil or black earth; from 5 to 20 % of peat; from 2.5 to 10 % of rocky material; the balance being sand. The method for producing this mixture comprises sifting the sandy or clayey soil or black earth using a screen having cells not exceeding 12 mm. The mixture is then fed under dry weather conditions into a drainage system or spread onto the subsoil in a layer having a thickness between 3 and 50 cm depending on the future use of the turf. This layer is applied from the centre of the lawn towards its edges while maintaining the slope of the subsoil or drainage system. The surface of the added or flattened mixture is then rolled using a wooden compactor that weighs up to 100 kg and comprises a drum with a diameter and a length varying from 80 to 120 cm and from 130 to 150 cm respectively. The mixture thus applied is further submitted to vapour treatment for 3 to 4 weeks in order to settle and watered daily in the absence of rain.

2.WO/1998/047763TRACTION SYSTEM FOR PROPELLER-DRIVEN TRANSPORT AEROPLANE

WO - 29.10.1998

Clasificación Internacional B64D 27/14 Nº de solicitud PCT/FR1998/000764 Solicitante SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION Inventor/a DUSSERRE-TELMON, Guy, Franck, Paul

The invention concerns a traction system for a propeller-driven transport aeroplane comprising at least a first and second pair of propellers (11, 12; 31, 32) mounted in the aeroplane wing plane. Each pair of propellers comprises two propellers symmetrically arranged on either side of the aeroplane central and longitudinal axis XX'. The first and second propeller pairs(11, 12; 31, 32) are driven independently of each other, respectively by first and second engine units (10, 30) arranged side by side in the aeroplane fuselage and by first and second independent transmission assemblies (13, 33).

3.WO/1997/009526TURBOJET THRUST REVERSER HAVING DOORS COMBINED WITH AN UPSTREAM SCOOP PANEL

WO - 13.03.1997

Clasificación Internacional F02K 1/68 Nº de solicitud PCT/FR1996/001359 Solicitante SOCIETE HISPANO-SUIZA Inventor/a GONIDEC, Patrick

A dual flow turbojet thrust reverser has pivoting doors (7) forming deflection members when operating in thrust reversing mode. Each door (7) is lined on its inner surface, in a closed position thereof, with an upstream panel (22) smoothing the fluid stream in direct jet mode. The upstream panel (22) which is not connected to the door (7) can rotate, when in thrust reversing mode, in a direction opposite to that of the door (7) so that its upstream edge is radially closer to the duct axis than its downstream edge, thus forming a scoop that picks up an inner portion of the stream to control the reverse flow layers and to provide for efficient thrust reversal.

4.WO/1999/002843SHOCKPROOF THRUST REVERSER

WO - 21.01.1999

Clasificación Internacional B64D 29/06 Nº de solicitud PCT/FR1998/001482 Solicitante HISPANO-SUIZA AEROSTRUCTURES Inventor/a BAUDU, Pierre, André, Marcel

The invention concerns an aircraft turbojet thrust reverser specially designed to resist shocks from objects coming from the turbo-shaft engines around which they are arranged, such as wrecks of vanes or disks, said shocks being capable of deforming the thrust reverser ring-shaped structure or break the stiffeners thereof. Said reverser is characterised in that the emergency locking systems (33) comprise each an articulated slide bolt (38) one end of which has the shape of a hook (40) partially enclosing the locking interface (43), the slide bolt (38) being automatically returned for closing by elastic means (47). Such arrangement enables to produce additional mechanical links capable of compensating deformations of the thrust reverser ring-shaped structure or the breakage of stiffeners.

5.WO/1993/004273TURBOREACTOR THRUST REVERSER HAVING A PROGRESSIVE CURVATURE DEFLECTING EDGE

WO - 04.03.1993

Clasificación Internacional F02K 1/56 Nº de solicitud PCT/FR1992/000802 Solicitante SOCIETE ANONYME HISPANO SUIZA Inventor/a CARIMALI, Félix

A reverse path (17) for the passage of flow reversed by a turboreactor thrust reverser is delimited on one side by deflecting edge (108) integral with a stationary part (1). The longitudinal sections (A, B, C, D) of the deflecting edge (108) have a progressive curvature from one lateral edge to the other of the reverse path such as to improve control of the reverse thrust layers.

6.WO/1997/030279JET ENGINE THRUST REVERSER WITH DOORS LINKED TO AN UPSTREAM PANEL

WO - 21.08.1997

Clasificación Internacional F02K 1/70 Nº de solicitud PCT/FR1997/000273 Solicitante SOCIETE HISPANO-SUIZA Inventor/a JEAN, Michel, Christian, Marie

A bypass jet engine thrust reverser comprising pivoting doors (7) integrated into the outer pod wall in the direct thrust position and forming deflecting buckets for thrust reversal. An internal upstream panel (20) lines the inner surface of each door (7) and is hinged to the same pivot (27) as the door (7). The linkage between the door (7) and the upstream panel (20) consists of an epicyclic gear train assembly comprising a planet gear (31) secured to the door (7), an outer sprocket wheel (34) secured to the upstream panel (20), and at least one freely rotatable planet pinion (33) secured to the fixed structure of the reverser. When a control means switches to the thrust reversal position, the door (7) and the upstream panel (20) pivotally rotate in opposite directions.

7.WO/2001/096711DEVICE FOR LOCKING HAMMER CLAMP BLADES ON A DISC

WO - 20.12.2001

Clasificación Internacional F01D 5/30 Nº de solicitud PCT/FR2001/001843 Solicitante SNECMA MOTEURS Inventor/a GOGA, Jean-Luc, Christian, Yvon

The invention concerns a device for locking hammer clamp blades in the groove (2) of a disc (1) of a gas turbine engine wheel comprising a body (15) whereof the cross-section is shaped to match the cross-section of the groove (2), a locking element (16) mounted radially mobile in a through hole provided in the body (15) and capable of being partly received in a lock housing (9a, 9b), and a screw for manoeuvring (17) the locking element (16). The locking element (16) comprises stops (32a) sliding in the windows (22a) of the body (15). The screw head (41) is large-sized and is radially locked between the base of the groove (2) and the seat (20) of the body (15).

8.WO/2001/067026SYSTEM FOR REACTIVE ARMOR OF MILITARY EQUIPMENT. SYSTEM FOR REACTIVE ARMOR OF A TURRET.

WO - 13.09.2001

Clasificación Internacional F41H 5/007 Nº de solicitud PCT/EA2001/000001 Solicitante GRIGORYAN, Valery Armenakovich Inventor/a GRIGORYAN, Valery Armenakovich

The inventive system relates to the protection of military equipment against shells and is directed at developing a modular protection. The system for reactive armor of a hull (1) and a turret (2) is embodied in the form of modules (3, 4, 5). A hull module (3) is embodied as a single unit assembled from load-carrying side rails (6) and cross ribs (7) which are rigidly connected to each other and form sections wherein protective blocks (8) are placed. The hull (2) modules are unified in the form of protective rigidly connected blocks (8). The protective blocks (8) comprise armored layers (9, 10) and form a cavity wherein one or several layers of active elements (11) can be arranged. Metal plates (12, 13) can be arranged in the cavity between the layers of active elements (11) and between the armored layer (9, 10) and the active elements (11). The armored layers (9, 10) can be made of various materials and embodied in the form of composite structures (14, 15). In addition, a layer of a protective material can be applied to the layer of protective elements (11), to the metal plates (12, 13) and to the cavity surface.

9.WO/1998/038425TURBOJET THRUST REVERSE SYSTEM WITH DOORS ASSOCIATED WITH A CONTROL SYNCHRONISING DEVICE

WO - 03.09.1998

Clasificación Internacional F02K 1/70 Nº de solicitud PCT/FR1998/000310 Solicitante HISPANO-SUIZA AEROSTRUCTURES Inventor/a BAUDU, Pierre, André, Marcel

The invention concerns a bypass turbojet thrust reverse system comprising pivoting doors (7a, 7b) integrated in direct jet in the outer wall of the fan air duct (15) and constituting flux deviating obstacles providing thrust reversal. At least two actuators (23) controlling the door (7a, 7b) movements are associated with a synchronising device (19) consisting of an electric motor (20) and its electronic power system (21) and a bezel box (22) connected by a transmission linkage (26) to each actuator (23) respectively. Thus the security of operation is ensured in the event that the door is not locked.

10.WO/1998/057056TURBOJET THRUST REVERSER HAVING DOORS WITH VARIABLE EXHAUST SECTION

WO - 17.12.1998

Clasificación Internacional F02K 1/70 Nº de solicitud PCT/FR1998/001200 Solicitante HISPANO-SUIZA AEROSTRUCTURES Inventor/a GONIDEC, Patrick

The invention concerns a turbojet thrust reverser comprising a fixed upstream ring-shaped structure (11) and a downstream ring-shaped structure (12) movable in translation between an upstream position wherein an upstream part of said downstream structure (12) is housed inside the upstream structure (11) and a downstream position wherein it produces a variation in the exhaust section between the turbojet primary cowl (15) and the downstream structure (12) radially inner wall. The downstream ring-shaped structure (12) further comprises doors (20) integrated in closed position, in direct jet, in the pod wall and deviating at least part of the turbojet exhaust flow, in unfolded position providing thrust reversal after the translation of the downstream structure (12).

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